EP0331603B1 - Airfoiled blade - Google Patents
Airfoiled blade Download PDFInfo
- Publication number
- EP0331603B1 EP0331603B1 EP89630026A EP89630026A EP0331603B1 EP 0331603 B1 EP0331603 B1 EP 0331603B1 EP 89630026 A EP89630026 A EP 89630026A EP 89630026 A EP89630026 A EP 89630026A EP 0331603 B1 EP0331603 B1 EP 0331603B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- airfoil
- blade
- section
- sections
- thickness
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/02—Formulas of curves
Definitions
- This invention relates to a propeller blade and more particularly a propeller blade comprised of a new airfoil family.
- a blade as defined in the precharacterizing portion of independent claim 1 is disclosed in GB-A-2 102 505.
- the known blade has a blunt, generally parabolic leading edge portion which on the pressure side fairs into a pressure surface which has a leading convex portion and on the suction side fairs into a convex suction surface, with both the pressure and suction surfaces merging into a blunt trailing edge.
- the disclosed airfoil sections range in shape from a thickness ratio of 0.04, with a maximum thickness at approximately 0.35 x/c and a maximum camber at approximately 0.50 x/c, at the blade tip, to a thickness ratio of 0.30, with a maximum thickness at approximately 0.310 x/c and a maximum camber at approximately 0.29 x/c, at the blade root.
- the blade disclosed in GB-A-2 102 505 provides advantages in the above respects over the NACA Series 16 blades but additional improvement is still desired.
- the object of the present invention is to create a blade incorporating a family of airfoil sections which provide high operating lift coefficients at take-off and efficient operating characteristics at cruising and loitering speeds.
- a blade having a root portion, and a tip portion, said blade comprising a plurality of airfoil sections, each section having along the entire length thereof, a cross sectional shape having a blunt parabolic leading edge and a relatively blunt trailing edge, said blade characterized by each airfoil section having a maximum thickness between about 38 % chord to about the 42 % chord, and a camber having an apogee at about a 45 % chord, and by said plurality of sections tapering from an airfoil section having a thickness ratio of twenty percent contiguous to the root of said blade to an airfoil section having a thickness ratio of two percent contiguous to the tip of said blade, and as said airfoil sections taper from said 20 % to said 2 % thickness ratio along said blade, the position of said maximum thickness of said airfoil sections varying progressively from said about 38 % chord line at the root of said blade to said about 42 % chord line at the tip of said blade.
- the novel blade of the invention minimizes take-off and cruise shock losses thereby providing superior aerodynamic performance to the NACA Series 16 airfoil in the Mach 0.50 to 0.70 range with less susceptibility to foreign object damage and handling problems.
- FIG. 1 a series of cross-sections of the airfoil blade 10 of the present invention is shown.
- the blade has a tip portion 15 and a root portion 20.
- Each airfoil section of the blade is identified by indicia comprising two numerals equal to the thickness ratio (thickness/length) multiplied by 1000.
- the uppermost airfoil section 23 is characterized by a thickness ratio of 0.023
- the second airfoil section 29 is characterized by a thickness ratio of 0.029
- the third airfoil section 39 is characterized by a thickness ratio of 0.039
- the fourth airfoil section 57 is characterized by a thickness ratio of 0.057
- the fifth airfoil section 85 is characterized by a thickness ratio of 0.085
- the sixth airfoil section 136 is characterized by a thickness ratio of 0.136
- the seventh airfoil section 206 is characterized by a thickness ratio of 0.206.
- the 23 airfoil cross-section is taken at a location approximately 0.90 of the blade longitudinal axis from the root portion 20 thereof.
- the 29 airfoil cross-section is taken at a location approximately 0.85 of the length of the blade longitudinal axis from the root portion 20 thereof.
- the 39 cross-section is taken at location approximately 0.76 of the length of the blade longitudinal axis from the root portion.
- the 57 cross-section is taken at approximately 0.53 of the length
- the 85 cross-section is taken at approximately 0.45 of the length
- the 136 section is taken at approximately 0.29 of the length
- the 206 section is taken at approximately 0.23 the length of the blade longitudinal axis from the root portion.
- chords of the airfoil sections are illustrated as being of a common length, design considerations regarding blade taper will dictate the relative sizes of the airfoil sections and the present invention shall not be limited to any specific size relationship between the airfoil sections.
- Cross-sections of the blade between the airfoil sections shown in Fig. 1 are defined by a transition surface connecting corresponding portions between any two adjacent airfoil shapes as is well known in the art.
- the airfoil cross-sections will, of course, be angularly displaced from one another in a manner well known in the art to import sufficient twist to the blade to establish varying blade angles of attack dictated by aerodynamic performance requirements.
- the following tables list precise dimensionless coordinates of a number of airfoil sections of an embodiment of a blade of the present invention.
- the x/c values are dimensionless locations on the blade chord line.
- the y/c upper are the dimensionless heights from the chord line to points on a blade suction surface.
- the y/c lower are the dimensionless heights from the chord line to points on a blade pressure surface.
- the t/c values are dimensionless heights from the chord line to the curvature of the mean line (i.e. camber) of each airfoil section.
- the shapes of the particular airfoil sections described below are shown in Fig. 4.
- Each airfoil section has a unique location of maximum thickness in conjunction with a camber having an apogee at about 0.45 x/c (See Fig. 3).
- the position of the maximum thickness of each section moves away from the airfoil section leading edge from the root portion 20 to the tip portion 15 of the blade (See Fig. 4).
- the maximum thickness of the 206 section is at about 0.3894 x/c.
- the maximum thickness of the 136 section is at about 0.3896 x/c.
- the maximum thickness of the 85 section is at about 0.3997 x/c.
- the maximum thickness of the 57 section is at about 0.4099 x/c.
- the maximum thickness of the 39 section is at about 0.42001 x/c.
- the maximum thickness of the 29 section is at about 0.42004 x/c.
- the maximum thickness of the 23 section is at about 0.42008 x/c.
- Each airfoil also has a relatively blunt leading edge and trailing edge compared to the NACA series 16 airfoil (see Fig. 4).
- Each of the airfoils is characterized by a relatively thick trailing edges as follows: the 23 section thickness is about .0023; the 29 section thickness is about .0029; the 39 section thickness is about .0038; the 57 section thickness is about .0056; the 85 section thickness is about .0084; the 136 section thickness is about .0133; and, the 206 section thickness is about .0201.
- the relatively thick trailing edges provide a blade that is easier to construct and handle compared to the NACA 16 blade which has a relatively thin and sharp trailing edge.
- the camber for each airfoil section of the invention depends generally on the desired lift coefficient for each airfoil section within the blade.
- Figure 2 shows the camber lines that each airfoil may utilize depending on such desired lift coefficient (CLD).
- the camber lines may be scaled (i.e. shaped similarly to the camber lines of Fig. 2 but on a different scale) depending on the desired lift coefficient.
- the 23 airfoil section has a desired CLD of about 0.31
- the 29 airfoil section has a desired CLD of about 0.33
- the 39 airfoil section has a desired CLD of about 0.32
- the 57 airfoil section has a desired CLD of about 0.288
- the 85 airfoil section has a desired CLD of about 0.20
- the 136 airfoil section has a desired CLD of about 0.10
- the 206 airfoil section has a desired CLD of about 0.09.
- the particular blade described above is designed to cruise optimally at about Mach 0.62 to 0.68.
- the camber and thickness of each section may be modified to achieve optimum blade loading for other desired mission profiles.
- Each thickness may utilize any of the described camber lines or any of a series of scaled camber lines having an apogee at about 0.45 x/c.
- the thickness ratios for each airfoil section may vary if such thicknesses are interpolated from the airfoil sections described and shown above (see Fig. 3).
- a particular blade may be designed to operate at mission profiles between Mach 0.50 to 0.70.
- the performance of the 23 airfoil section of the airfoil family of the present invention is compared with performance of a comparable section of a conventional NACA Series 16 blade below: where Mn is the speed of the airfoil section, CI is the lift coefficient, Cd is the drag coefficient and Mns is the speed of the air flow at the surface of the blade.
- Mn the speed of the airfoil section
- Cd the drag coefficient
- Mns is the speed of the air flow at the surface of the blade.
- the present invention provides essentially equal performance in terms of lift and drag to the NACA 16 airfoil blade.
- the HS2 airfoil section shows significant improvement at cruise, loiter and take-off relating to the Mns.
- the NACA Series 16 blade shows higher Mach numbers (Mns) above the speed of sound. Such higher Mach numbers cause shock which causes boundary layer separation, and increased drag and noise.
- the present invention provides essentially equal performance in terms of lift and drag to the NACA 16 airfoil blade.
- the HS2 airfoil section shows significant improvement at cruise and take-off relating to the Mns.
- the higher Mach numbers on the blade surface of the NACA Series 16 blade create shocks which causes boundary layer separation, and increased drag and noise.
- the present invention minimizes the shocks encountered.
- the airfoil family of this invention offers the following advantages over conventional airfoils.
- the relatively blunt leading edges of the airfoil sections minimize foreign object damage and are also easier to manufacture than the sharper leading edges of the NACA Series 16 blades.
- the relatively blunt trailing edge minimizes blade handling problems.
- a blade may be designed to provide optimal loading for a particular mission profile from between Mach 0.50 to 0.70.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Toys (AREA)
- Lubricants (AREA)
- Materials For Photolithography (AREA)
- Enzymes And Modification Thereof (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US163901 | 1988-02-29 | ||
US07/163,901 US4830574A (en) | 1988-02-29 | 1988-02-29 | Airfoiled blade |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0331603A2 EP0331603A2 (en) | 1989-09-06 |
EP0331603A3 EP0331603A3 (en) | 1990-07-25 |
EP0331603B1 true EP0331603B1 (en) | 1994-06-01 |
Family
ID=22592090
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP89630026A Expired - Lifetime EP0331603B1 (en) | 1988-02-29 | 1989-02-14 | Airfoiled blade |
Country Status (8)
Country | Link |
---|---|
US (1) | US4830574A (zh) |
EP (1) | EP0331603B1 (zh) |
JP (1) | JPH0211493A (zh) |
CN (1) | CN1017792B (zh) |
BR (1) | BR8900885A (zh) |
CA (1) | CA1320715C (zh) |
DE (2) | DE331603T1 (zh) |
ES (1) | ES2010649T3 (zh) |
Families Citing this family (44)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4941803A (en) * | 1989-02-01 | 1990-07-17 | United Technologies Corporation | Airfoiled blade |
US5433586A (en) * | 1991-03-27 | 1995-07-18 | Cessna Aircraft Company | Tapered propeller blade design |
US5209643A (en) * | 1991-03-27 | 1993-05-11 | The Cessna Aircraft Company | Tapered propeller blade design |
US5188508A (en) * | 1991-05-09 | 1993-02-23 | Comair Rotron, Inc. | Compact fan and impeller |
US5417548A (en) | 1994-01-14 | 1995-05-23 | Midwest Research Institute | Root region airfoil for wind turbine |
US5562420A (en) * | 1994-03-14 | 1996-10-08 | Midwest Research Institute | Airfoils for wind turbine |
US5791878A (en) * | 1997-03-10 | 1998-08-11 | United Technologies Corporation | Airfoiled blade for cargo transport aircraft |
FR2765187B1 (fr) * | 1997-06-25 | 1999-08-27 | Onera (Off Nat Aerospatiale) | Profil de pale pour voilure tournante d'aeronef et pale pour voilure tournante presentant un tel profil |
US5911559A (en) * | 1997-09-16 | 1999-06-15 | United Technologies Corporation | Airfoiled blade for a propeller |
US6068446A (en) * | 1997-11-20 | 2000-05-30 | Midwest Research Institute | Airfoils for wind turbine |
JP3483447B2 (ja) * | 1998-01-08 | 2004-01-06 | 松下電器産業株式会社 | 送風装置 |
US6565334B1 (en) | 1998-07-20 | 2003-05-20 | Phillip James Bradbury | Axial flow fan having counter-rotating dual impeller blade arrangement |
US6129528A (en) * | 1998-07-20 | 2000-10-10 | Nmb Usa Inc. | Axial flow fan having a compact circuit board and impeller blade arrangement |
US6856941B2 (en) | 1998-07-20 | 2005-02-15 | Minebea Co., Ltd. | Impeller blade for axial flow fan having counter-rotating impellers |
US6607164B2 (en) | 2001-10-22 | 2003-08-19 | Toyota Motor Sales, U.S.A., Inc. | Wing airfoil |
DE10206530A1 (de) * | 2002-02-16 | 2003-08-28 | Schottel Gmbh & Co Kg | Antrieb für Wasserfahrzeuge |
CA2488151C (en) * | 2002-06-05 | 2009-04-28 | Aloys Wobben | Rotor blade for a wind power plant |
US6948910B2 (en) | 2002-07-12 | 2005-09-27 | Polacsek Ronald R | Spiral-based axial flow devices |
DE10319246A1 (de) * | 2003-04-28 | 2004-12-16 | Aloys Wobben | Rotorblatt einer Windenergieanlage |
EP1717644B1 (en) | 2005-04-26 | 2011-04-13 | Brother Kogyo Kabushiki Kaisha | Developer cartridge for image-forming device |
GB0510417D0 (en) * | 2005-05-21 | 2005-06-29 | Rotech Holdings Ltd | Improved turbine |
CN101263277B (zh) | 2005-07-15 | 2011-11-30 | 维斯塔斯风力***有限公司 | 风轮机叶片 |
US7547193B2 (en) | 2005-07-22 | 2009-06-16 | Sikorsky Aircraft Corporation | Rotor blade assembly with high pitching moment airfoil section for a rotary wing aircraft |
JP5067104B2 (ja) * | 2007-10-03 | 2012-11-07 | トヨタ自動車株式会社 | 車両下部構造 |
ES2330500B1 (es) * | 2008-05-30 | 2010-09-13 | GAMESA INNOVATION & TECHNOLOGY, S.L. UNIPERSONAL | Pala de aerogenerador con elementos hipersustentadores. |
US9340277B2 (en) * | 2012-02-29 | 2016-05-17 | General Electric Company | Airfoils for use in rotary machines |
CN103244359B (zh) * | 2013-05-30 | 2016-04-13 | 国电联合动力技术有限公司 | 一种大型风机的中等厚度翼型叶片 |
CN103321857B (zh) * | 2013-07-08 | 2015-05-06 | 国电联合动力技术有限公司 | 一种大型风机的大厚度钝尾缘翼型叶片 |
CN103482054B (zh) * | 2013-08-14 | 2015-07-01 | 西北工业大学 | 一种匹配全翼太阳能无人机的低雷诺数翼型 |
CN104044729B (zh) * | 2014-05-27 | 2016-04-06 | 北京航空航天大学 | 一种高高空螺旋桨装置 |
RU2685372C2 (ru) * | 2014-08-21 | 2019-04-17 | ТИХЕРИНА Хуан Херардо НАРВАЭС | Аэродинамический профиль (варианты) и крыло |
CN105564632A (zh) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | 一种高升力自然层流翼型 |
US9868525B2 (en) * | 2015-09-25 | 2018-01-16 | The Boeing Company | Low speed airfoil design for aerodynamic improved performance of UAVs |
CN106143850A (zh) * | 2016-06-17 | 2016-11-23 | 中国舰船研究设计中心 | 螺旋桨桨叶剖面及其应用方法 |
US10358926B2 (en) | 2017-08-11 | 2019-07-23 | General Electric Company | Low-noise airfoil for an open rotor |
DE102017124861A1 (de) | 2017-10-24 | 2019-04-25 | Wobben Properties Gmbh | Rotorblatt einer Windenergieanlage und Verfahren zu dessen Auslegung |
CN207917131U (zh) * | 2018-01-31 | 2018-09-28 | 深圳市大疆创新科技有限公司 | 螺旋桨、动力组件及飞行器 |
CN108583871A (zh) * | 2018-06-25 | 2018-09-28 | 李竟儒 | 一种使直升飞机气流上升的旋翼 |
CN109110124A (zh) * | 2018-09-03 | 2019-01-01 | 南京航空航天大学 | 一种新型旋翼桨叶 |
US11999466B2 (en) * | 2019-11-14 | 2024-06-04 | Skydio, Inc. | Ultra-wide-chord propeller |
RU2752502C1 (ru) * | 2020-12-18 | 2021-07-28 | Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") | Аэродинамический профиль несущего элемента летательного аппарата |
RU2762464C1 (ru) * | 2021-05-14 | 2021-12-21 | Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") | Аэродинамический профиль несущего элемента летательного аппарата |
US11952912B2 (en) * | 2022-08-24 | 2024-04-09 | General Electric Company | Turbine engine airfoil |
US20240092481A1 (en) * | 2022-09-16 | 2024-03-21 | Hydronalix, Inc. | Ceramic propeller |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2709052A (en) * | 1952-04-15 | 1955-05-24 | Charles J Fletcher | Spanwise flow control of fluid swept lifting surfaces |
US4459083A (en) * | 1979-03-06 | 1984-07-10 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Shapes for rotating airfoils |
FR2463054A1 (fr) * | 1979-08-10 | 1981-02-20 | Aerospatiale | Profil de pale pour voilure tournante d'aeronef |
FR2490586A1 (fr) * | 1980-09-24 | 1982-03-26 | Aerospatiale | Profil de pale pour voilure tournante d'aeronef |
US4519746A (en) * | 1981-07-24 | 1985-05-28 | United Technologies Corporation | Airfoil blade |
US4412664A (en) * | 1982-06-25 | 1983-11-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Family of airfoil shapes for rotating blades |
EP0103478A1 (en) * | 1982-09-13 | 1984-03-21 | Ian James Gilchrist | Airfoil |
DE3310937C2 (de) * | 1982-10-09 | 1984-10-31 | Dornier Gmbh, 7990 Friedrichshafen | Propellerblatt, insbesondere für den Vortrieb von Luftfahrzeugen |
US4611773A (en) * | 1982-12-30 | 1986-09-16 | The Boeing Company | Tapered thickness-chord ratio wing |
US4569633A (en) * | 1983-04-18 | 1986-02-11 | United Technologies Corporation | Airfoil section for a rotor blade of a rotorcraft |
FR2590229B1 (fr) * | 1985-11-19 | 1988-01-29 | Onera (Off Nat Aerospatiale) | Perfectionnements apportes aux helices aeriennes en ce qui concerne le profil de leurs pales |
-
1988
- 1988-02-29 US US07/163,901 patent/US4830574A/en not_active Expired - Lifetime
-
1989
- 1989-01-17 CA CA000588405A patent/CA1320715C/en not_active Expired - Fee Related
- 1989-02-14 EP EP89630026A patent/EP0331603B1/en not_active Expired - Lifetime
- 1989-02-14 DE DE198989630026T patent/DE331603T1/de active Pending
- 1989-02-14 DE DE68915583T patent/DE68915583T2/de not_active Expired - Fee Related
- 1989-02-14 ES ES89630026T patent/ES2010649T3/es not_active Expired - Lifetime
- 1989-02-20 JP JP1040134A patent/JPH0211493A/ja active Pending
- 1989-02-27 BR BR898900885A patent/BR8900885A/pt not_active IP Right Cessation
- 1989-02-28 CN CN89100932A patent/CN1017792B/zh not_active Expired
Also Published As
Publication number | Publication date |
---|---|
ES2010649T3 (es) | 1994-08-16 |
ES2010649A4 (es) | 1989-12-01 |
JPH0211493A (ja) | 1990-01-16 |
CN1017792B (zh) | 1992-08-12 |
CA1320715C (en) | 1993-07-27 |
DE68915583D1 (de) | 1994-07-07 |
EP0331603A3 (en) | 1990-07-25 |
BR8900885A (pt) | 1989-10-17 |
DE68915583T2 (de) | 1994-09-22 |
DE331603T1 (de) | 1990-02-08 |
US4830574A (en) | 1989-05-16 |
EP0331603A2 (en) | 1989-09-06 |
CN1036536A (zh) | 1989-10-25 |
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